US4146780A - Antiaircraft weapons system fire control apparatus - Google Patents

Antiaircraft weapons system fire control apparatus Download PDF

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Publication number
US4146780A
US4146780A US05/751,654 US75165476A US4146780A US 4146780 A US4146780 A US 4146780A US 75165476 A US75165476 A US 75165476A US 4146780 A US4146780 A US 4146780A
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aircraft
gun
target aircraft
signals corresponding
maneuver
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US05/751,654
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Pierre M. Sprey
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Ares Inc
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Ares Inc
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Priority to US05/751,654 priority Critical patent/US4146780A/en
Priority to GB596/78A priority patent/GB1568915A/en
Priority to BE184563A priority patent/BE863223A/fr
Priority to NL7800980A priority patent/NL7800980A/xx
Priority to FR7802543A priority patent/FR2415791A1/fr
Priority to DE19782805903 priority patent/DE2805903A1/de
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G5/00—Elevating or traversing control systems for guns
    • F41G5/08—Ground-based tracking-systems for aerial targets

Definitions

  • This invention relates generally to antiaircraft gunfire control systems, and more specifically to apparatus for predicting the flight path of maneuvering target aircraft.
  • Typical antiaircraft weapons systems include ranging and tracking means for acquiring target aircraft and monitoring their movement, a fire control system, and gun moving or laying means for directing a gun or guns along a projected target aircraft intercept path in response to signals from the fire control system.
  • a fire control system includes a computer for continuously calculating, from inputs from the ranging and tracking means and also from other inputted information, such as ballistics of the gun projectiles, a sequence of projected aircraft-gun projectile intercept positions.
  • various correction factors for example, wind velocity or variation of projectile ballistic path with angle of elevation, may be supplied to, and be acted on by, the computer in calculating these projected intercept positions.
  • gun fire control apparatus in an antiaircraft weapons system having at least one projectile firing gun, target aircraft tracking and ranging means having electrical output signals corresponding to target aircraft position and range and signal responsive gun laying means for aiming the gun, includes load factor inputting means for enabling selective, manual generation of electrical signals corresponding to estimated target aircraft maneuver load factors and roll angle inputting means for enabling selective, manual generation of electrical signals corresponding to estimated target aircraft roll angles.
  • fire control computer means connected for receiving the electrical signals corresponding to target aircraft position and range and to the electrical signals corresponding to the estimated target aircraft maneuver load factors and roll angles. In response to the electrical signals the fire control computer means calculates a progression of target aircraft-gun projectile intercept points and supplies electrical controlling signals corresponding thereto to the gun laying means.
  • the fire control computer means includes maneuver correction means, responsive to the tracking and ranging means and the electrical signals corresponding to estimated target aircraft maneuver load factors and roll angles, for calculating a correction to the predicted progression of future aircraft position, manual switch means in operative relationship with the roll factor and roll angle inputting means for selectively activating the maneuver correction means, and iteration means, in operative relationship with the switch means, the linear extrapolation means and the maneuver correction means, for calculating a progression of corrected aircraft projectile intercept positions and for supplying electrical controlling signals corresponding thereto to the gun laying means.
  • maneuver correction means responsive to the tracking and ranging means and the electrical signals corresponding to estimated target aircraft maneuver load factors and roll angles, for calculating a correction to the predicted progression of future aircraft position
  • manual switch means in operative relationship with the roll factor and roll angle inputting means for selectively activating the maneuver correction means
  • iteration means in operative relationship with the switch means, the linear extrapolation means and the maneuver correction means, for calculating a progression of corrected aircraft projectile intercept positions and for supplying electrical controlling signals
  • This invention achieves a very significant improvement in aircraft flight path prediction by utilizing more input information concerning the likely target aircraft future flight path than prior fire control systems.
  • This additional information includes the inputs of aircraft roll angle and aircraft load factor (often called aircraft "g").
  • the roll angle is observed visually, estimated and entered in the fire control computer via manual means.
  • the aircraft load factor is observed visually, estimated and entered into the fire control computer via manual means.
  • FIG. 1 is an overall pictorial view of the apparatus of this invention
  • FIG. 2 is a perspective view of a command console showing manual means for inputting estimated magnitudes of aircraft maneuvers;
  • FIG. 3 is a diagram of typical weapon delivery maneuvers by an attacking aircraft
  • FIG. 4 diagrams various specific maneuvers by a maneuvering aircraft
  • FIG. 5 is a plot of miss distance as a function of time for a gun firing a projectile against a maneuvering aircraft
  • FIG. 6 is a logic block diagram of the automatic fire control and manual input means
  • FIG. 7 is a geometric illustration of an aircraft maneuver correction
  • FIG. 8 is a block diagram of a prior art fire control system showing incorporation of apparatus according to this invention.
  • FIG. 1 schematically diagrams major portions of an antiaircraft weapon system 10 in accordance with this invention.
  • a tracking and ranging portion 12 of the weapon system 10 includes a manually operated optical sight 14 and a manually directed range finder 16.
  • the range finder 16 may utilize a laser and is adapted to measure the distance to a target aircraft 18 many times per second. Both the optical sight 14 and the range finder 16 provide electrical output signals corresponding respectively to the target aircraft position and range.
  • a weapons system gun (or guns) 20 includes conventional azimuthal and elevational laying means 22 and 24, respectively, both of which are responsive to fire control output signals (as described below) for aiming the gun toward the target aircraft 18.
  • a common power supply 26 furnishes the necessary power to all portions of the system 10.
  • a gun commander console 28 shown in FIG. 2, and hereinafter more particularly described contains both load factor inputting means 30 for enabling selective, manual generation of electrical signals corresponding to estimated target aircraft maneuver load factors and roll angle inputting means 32 for enabling selective, manual generation of electrical signals corresponding to estimated target aircraft roll angles.
  • the load, or "g" factor, of an aircraft is the total force exerted on the aircraft and is a vectoral sum of both gravitational force and the centrifugal force due to maneuvering.
  • the magnitude of the load factor corresponds, as hereinafter described, to a radius of curvature which defines a target aircraft flight path at a given speed.
  • the roll angle of an aircraft is the angle between the wings of the aircraft and a horizontal line passing transversely through the aircraft fuselage.
  • Such means 36 is additionally connected for receiving electrical signals corresponding to target aircraft position and range from the tracking and ranging portion 12. From the signals thus received, the computer means 36 calculates a series or progression of target aircraft-gun projectile intercept points or positions, and supplies electrical controlling signals corresponding thereto to the gun laying means 22 and 24 for causing aiming of the gun 20.
  • the load factor inputting means 30 includes a turnable load factor control knob 38, identified as "G”, which is connected, for example, to a conventional single turn potentiometer or multi-position switch, not shown.
  • G turnable load factor control knob 38
  • This enables generation and transmission to the fire control computer means 36 of an electrical signal corresponding to the selected position of the "G" control knob 38 with respect to a calibrated scale 40 on a console face 42, when a manually operated input switch 44 is activated.
  • the input switch 44 is preferably a multi-pole switch connected in electrical series with the potentiometer or switch associated with the "G" control knob 38 and, when manually depressed, closes a circuit to the fire control computer means 36. Since the expected range of aircraft load factors is from about 0 to a maximum of 9 g's the scale 40 is accordingly calibrated.
  • the roll angle inputting means 32 includes a turnable control knob 46, identified as "Roll”.
  • the roll control knob 46 is also preferably connected to a conventional single turn potentiometer or multi-position switch, not shown, such that for each selected position of the control knob 46, with respect to an associated calibrated scale 48 on the console face 42, a corresponding electrical signal is also transmitted to the fire control computer means 36 when the manual switch 44 is depressed.
  • the switch 44 has one pole for interconnecting with the fire control computing means 36 the potentiometer associated with the load factor control knob 38 and another pole for so interconnecting the potentiometer associated with the roll angle control knob 46.
  • the expected range of roll angle through the course of an attacking aircraft maneuver is between minus 90 degrees and plus 90 degrees, the scale 48 being calibrated accordingly.
  • the estimated future direction of aircraft roll movement is indicated by the plus or minus sign of the aircraft roll angle.
  • a power switch 50 is provided in the console 28 to disconnect the load factor inputting means 30 and the roll angle inputting means 32 when the console is not in use.
  • aircraft maneuvering information is selectively introduced into the fire control computing means 36 at the initiation of an aircraft maneuver and continuously thereafter.
  • This maneuvering information is, as noted above, in the form of load factor and roll angle estimates, which are inputted into the fire control computer means 36 by the means 30 and 32, respectively, for each phase of an aircraft attack, as described below.
  • load factor and roll factor estimates are visual observation of the aircraft maneuver by an operator as well as prior knowledge, by the operator, of attack tactics of target aircraft.
  • observed relative misses of tracer-type projectiles may be used to improve the load factor and roll angle estimates.
  • Phase I represents a roll-in by the target aircraft 18, which is flying at a cruise speed of about 155 to 230 m/sec (300 to 450 knots) and at an altitude from about 1219m to 3658m (4,000 to 12,000 feet), just as aircraft comes abreast of a ground target 54.
  • the Phase I roll-in uses a bank or roll of 1 to 2 g's to turn through 60 to 120 degrees (angle A, FIG. 3) of heading from an initial aircraft flight path 56 or 58 to a dive flight path 60.
  • the aircraft 18 simultaneously dives to achieve about a 30 to 45 degree diving angle (line 60, Phase II).
  • the aircraft 18 is assumed to maintain a zero roll attitude to adjust the dive angle and stabilize the target 58 in the aircraft's bomb sight before bomb release at a point 62.
  • the aircraft 18 performs a 3 to 5 g pull-up from the dive, in a nearly zero roll attitude, until the aircraft nose passes through a horizontal plane 64.
  • the aircraft 18 then either escapes in a level flight path 66 or continues pulling up to establish a climbing path 68.
  • the aircraft typically performs evasive maneuvers, such as "jinking" or weaving, at load factors of 2 to 3 g's. Maneuvering load factors pulled along exit paths are ordinarily less than those during the initial pull-up to the horizontal plane 64 to avoid excessive speed loss during climbout.
  • FIG. 4a depicts the aircraft 18 banking in level flight, with a roll angle B and a lift vector 70 pointing in the direction of a radius of curvature R of a circular flight path 74.
  • a level turn by an attacking aircraft is rare. More commonly, an attack aircraft will either dive or climb while performing a roll. This usually occurs in Phase I of the attack, as shown in FIG. 4b where R' is the radius of a resultant curved flight path 76.
  • a wings-level pull-up shown in FIG. 4c is typically performed at the end of attack Phase II, the curvature R" of an aircraft flight path 78 being in a vertical plane.
  • Inputting of the load factor and the roll angles of the aircraft at the initiation of a maneuver by an attacking aircraft is particularly advantageous because, as is well known, aircraft experience a finite aerodynamic lag between the time attitude is changed and the onset of an actual change in the flight path.
  • maneuvering inputs to the computer at the instant an aircraft attitude change is observed provide the computer with information regarding the probable future flight path of the aircraft before the aircraft actually changes its flight direction. Because such maneuvering inputs anticipate the actual turn by the aircraft, the fire control computer means 36 can be adapted to compensate for human response in manipulating the manual input controls.
  • Typical operation of the control console 28 in association with the fire control computer means 36 is as follows: A gunner manually aims the optical sight 14 at the target aircraft 18 as soon as it is seen and continues to track the aircraft for the duration of the engagement. Upon acquiring and beginning to track the target aircraft 18, the gunner activates the range finder 16 to measure the aircraft's range. Concurrently with such tracking and ranging, a second gunner or gun commander watches the target aircraft 18 for maneuvers. Upon detecting a change in aircraft roll angle, for example, the gun commander turns the console roll angle input knob 46 to the appropriate scale position corresponding to the observed target roll angle.
  • the gun commander may preset the load factor and/or roll angle input knobs 38, 46 to levels anticipated as characteristic of the next attack phase. For instance, prior to initial roll-in (Phase I, FIG. 3) the commander may set the load factor input knob 38 to about 11/2 g's, since the load factor is expected, from experience, to be about 1 to 2 g's. Or, after the roll-in phase has been completed, the commander may then set the knob 38 to about 4 g's, anticipating the Phase III pull-up load factor will be between 3 and 4 g's.
  • Accurate correction to generally conventional, constant speed, linear extrapolation of target aircraft flight path during the time of flight of a projectile is essential, particularly at long range, if a high target hit and kill probability is to be achieved.
  • FIG. 5 plots calculated target miss distance as a function of projectile time of flight for a typical range of Phase I and II maneuvers when only such an extrapolation is used.
  • Miss distance as used herein, is defined as the distance between the actual position of an aircraft performing a maneuver and the position the aircraft would be at had it continued a straight line, constant speed flight; it is the amount by which a fired projectile will miss a maneuvering aircraft when only a straight line, constant speed extrapolation, without compensation for maneuvering, is used to calculate projected flight paths.
  • the fire control computing means 36 continuously receives target aircraft data from the tracking and ranging means 12, in the form of range, r, azimuthal angle, ⁇ , and elevation angle, ⁇ , the angles being in polar coordinates.
  • target aircraft data from the tracking and ranging means 12, in the form of range, r, azimuthal angle, ⁇ , and elevation angle, ⁇ , the angles being in polar coordinates.
  • Such data points are first transformed by the fire control computer means 36 to rectilinear coordinates X, Y and Z by a conventional coordinate converter 84, exemplified, for example, in U.S. Pat. No. 3,766,826 by H. M. A. Salomonsson.
  • the X, Y and Z data from the coordinate converter 84 is smoothed or averaged, to yield coordinates Xs, Ys and Zs which are used to obtain target aircraft component velocities x V s , y V s and z V s .
  • This is accomplished by X, Y and Z axis filter and velocity generators 86, 88 and 90, respectively.
  • the smoothing may be a simple average of several of the latest positional coordinates.
  • the velocity generator which may include an integrator, may be a conventional type such as described in above cited Salomonsson patent.
  • Equations utilized in the filter and velocity generators 86, 88 and 90 are:
  • Velocity and position data from the filter and velocity generators 86, 88 and 90 is directed to a linear extrapolation means 92 which calculates an aircraft future position in X, Y and Z coordinates, using separate X, Y and Z axis multipliers 94, 96 and 98 and adders 100, 102 and 104 for each coordinate, according to the equation:
  • X 1 linearly extrapolated target position in the X coordinate
  • t number of seconds of future path to be extrapolated.
  • the iteration means 120 calculates a fire control solution based only on the constant speed, linear extrapolation of the aircraft flight path given by X 1 , Y 1 and Z 1 , and as is sufficient if the target aircraft 18 is not maneuvering.
  • a maneuver-uncorrected fire control solution is calculated by iterating the value of t, the time period over which the target aircraft path is extrapolated, until the projectile time of flight, t f , to the future aircraft position (at time t) is equal to t.
  • t is iterated until the following generalized equation is satisfied:
  • the function t f which may be different for various types of guns and projectiles, is determined and stored in a ballistic storage register 122 such that it is accessible to the iteration means 120.
  • a second coordinate converter 124 translates these rectilinear coordinates (equation 6) back into polar coordinate r 1 , ⁇ 1 , ⁇ 1 entered at the gun 20.
  • Signals generated by the computer means 36 and corresponding to such polar coordinates, represent the final superelevation and lead pointing angle commands to the laying means 22 and 24 for training the gun 20 so that fired projectiles will interecept the target aircraft.
  • Ballistic corrections for wind, velocity ambient temperature, etc. may be provided by storing, in the register 122, sets of different functions t f , each t f corresponding to a different condition of wind, temperature, etc.
  • the weapon system 10 when tracking or firing at non-maneuvering target aircraft (with the switch 44 open or with no inputs from the console 28) the weapon system 10 operates in a generally conventional manner.
  • an operator depresses the console switch 44 to activate the maneuver correction means 118, and input thereinto an estimated load factor signal corresponding to a selected setting of the manual control knob 38 (in n g's) and an estimated roll angle signal corresponding to a selected setting of the control knob 46 (in ⁇ ⁇ degrees).
  • This causes a maneuvering correction, which may be curvilinear, to be applied to the constant velocity straight line extrapolation of the target aircraft path in order that a more accurate fire control solution is attained.
  • the maneuver correction means 118 includes a processor 126 which calculates the magnitude of the maneuver correction perpendicular to the aircraft velocity vector.
  • FIG. 7 illustrates a maneuver correction in an X, Y, Z coordinate system, A(i) being the position of the target aircraft at the beginning of the maneuver, A (i + t/ ⁇ ) being the target aircraft position at a later time, t, if no maneuver were performed and B (i + t/ ⁇ ) being the target aircraft position if the maneuver is performed.
  • a line 128 connecting the positions A(i) and A(i + t/ ⁇ ) represents the initial aircraft velocity vector; whereas, the magnitude of the maneuver correction is indicated by a double headed arrow 130.
  • the basis of the processor 126 calculations may be an assumed circular aircraft flight path having a radius, R, perpendicular to the aircraft velocity vector (line 128) in a plane 132 of maneuver (FIG. 7).
  • the mathematical representation of the maneuver correction vector, C(t, ⁇ , n), is given by:
  • the plane 132 of the maneuver rotates about the aircraft flight vector 128 and the angle, ⁇ , this plane makes with the vertical axis Z, is then given by:
  • the maneuver correction vector C(t, ⁇ ,n) is next resolved, by the processor 126, into rectangular coordinates
  • X, Y, and Z coordinate adders 134, 136 and 138 combine (when the switch 44 is closed) these maneuver correction components with the linearly extrapolated target position X,Y,Z, from the adders 100, 102 and 104, according to the following equation:
  • X m is the maneuver corrected extrapolation of target position in the X coordinates and C x (t, ⁇ ,n) represents the X component of the deviation from linear motion.
  • This curvilinear corrected position of the target aircraft is next passed to the iteration means 120 for determination of the solution by means of the functional equation:
  • the fire control means 36 calculates a series of such intercept positions or points in a substantially continuous manner, as the maneuvering target aircraft is tracked.
  • the gun 20 is likewise continuously trained by the laying means 22, 24 to lead the aircraft by the calculated amount so that any time firing is initiated a high target hit and kill probability exists.
  • the logic blocks representing the functions to be performed may preferably each be separate computing elements in order to reduce computer cost and provide for faster calculation as is well known in the art.
  • maneuver correction (Equation 7) may have to be introduced at a different point in the apparatus and at a different step in the data processing sequence.
  • the proper point and step to introduce the maneuver correction is dictated by the configuration of the preexisting systems, and can readily be determined by a person skilled in the art of fire control computers.
  • the Salomansson system 140 accomodates linear motion of a target aircraft by calculating a set of aim-off correction signals X t , Y t and Z t which are added to otherwise controlling signals X m , Y m and Z m by X, Y and Z coordinate axis adders 142, 144 and 146 when switch contacts 148, 150 and 152 are closed.
  • the resulting signals X k , Y k , Z k actually control training of an associated gun or guns (not shown).
  • the Salomansson (or similar) system 140 can be modified to provide maneuvering corrections by the addition of a maneuver correction processor 126a (similar to the above described processor 126) and the console 28. This may be accomplished by connecting the velocity output V x , V y , V x , of Salomansson X, Y and Z coordinate axis retaining circuits 154, 156 and 158 to the processor 126a, through X, Y and Z axes electrical wires 160, 162 and 164 (FIG. 8), and connecting the processor 126a to the Salomansson adders 142, 144 and 146 via X, Y and Z axes electrical wires 166, 168 and 170 though contacts 106, 108 and 110 respectively of the switch 44.
  • a maneuver correction processor 126a similar to the above described processor 126) and the console 28. This may be accomplished by connecting the velocity output V x , V y , V x , of Salomansson X, Y and
  • the processor 126a accepts roll and g signals from the control knobs 38 and 46 on the console 28 when the switch 44 is closed, in order to enable calculating of a maneuver correction C x , C y , C z as above described.
  • the adders 142, 144 and 146 then combine the controlling signals X m , Y m and Z m with both the aim-off correction signals X t , Y t and Z t and the maneuver correction signals C x , C y , C z to yield new signals X k ', Y k ', Z k ' for aiming the gun.

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  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US05/751,654 1976-12-17 1976-12-17 Antiaircraft weapons system fire control apparatus Expired - Lifetime US4146780A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US05/751,654 US4146780A (en) 1976-12-17 1976-12-17 Antiaircraft weapons system fire control apparatus
GB596/78A GB1568915A (en) 1976-12-17 1978-01-07 Antiaircraft weapons system
BE184563A BE863223A (fr) 1976-12-17 1978-01-23 Appareil de conduite de tir pour un systeme d'artillerie antiaerien
NL7800980A NL7800980A (nl) 1976-12-17 1978-01-26 Vuurleiding-stelsel voor een antivliegtuig- wapenstelsel.
FR7802543A FR2415791A1 (fr) 1976-12-17 1978-01-30 Appareil de commande de tir d'armes anti-aeriennes
DE19782805903 DE2805903A1 (de) 1976-12-17 1978-02-13 Schussteuerungseinrichtung fuer ein flugzeugabwehr-waffensystem

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US05/751,654 US4146780A (en) 1976-12-17 1976-12-17 Antiaircraft weapons system fire control apparatus
GB596/78A GB1568915A (en) 1976-12-17 1978-01-07 Antiaircraft weapons system
NL7800980A NL7800980A (nl) 1976-12-17 1978-01-26 Vuurleiding-stelsel voor een antivliegtuig- wapenstelsel.
FR7802543A FR2415791A1 (fr) 1976-12-17 1978-01-30 Appareil de commande de tir d'armes anti-aeriennes
DE19782805903 DE2805903A1 (de) 1976-12-17 1978-02-13 Schussteuerungseinrichtung fuer ein flugzeugabwehr-waffensystem

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BE (1) BE863223A (fr)
DE (1) DE2805903A1 (fr)
FR (1) FR2415791A1 (fr)
GB (1) GB1568915A (fr)
NL (1) NL7800980A (fr)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4266463A (en) * 1978-01-18 1981-05-12 Aktiebolaget Bofors Fire control device
US4320287A (en) * 1980-01-25 1982-03-16 Lockheed Electronics Co., Inc. Target vehicle tracking apparatus
US4528891A (en) * 1981-10-14 1985-07-16 Societe Nationale Industrielle Aerospatiale Firing control system for a direct firing weapon mounted on a rotary-wing aircraft
US4787291A (en) * 1986-10-02 1988-11-29 Hughes Aircraft Company Gun fire control system
US4794235A (en) * 1986-05-19 1988-12-27 The United States Of America As Represented By The Secretary Of The Army Non-linear prediction for gun fire control systems
US4823674A (en) * 1985-08-19 1989-04-25 Saab Instruments Aktiebolag Anti-aircraft sight
DE3401090C1 (en) * 1984-01-13 1991-05-02 Esg Elektronik System Gmbh Monitoring aircraft projectile or missile - using two extrapolation units to predict flight path
US5420582A (en) * 1989-09-15 1995-05-30 Vdo Luftfahrtgerate Werk Gmbh Method and apparatus for displaying flight-management information
US5732289A (en) * 1993-12-28 1998-03-24 Nikon Corporation Detecting apparatus
US5900577A (en) * 1997-01-29 1999-05-04 Zdf Import Export Inc Modular, multi-caliber weapon system
US6199471B1 (en) * 1999-05-21 2001-03-13 The United States Of America As Represented By The Secretary Of The Navy Method and system for determining the probable location of a contact
US20030141364A1 (en) * 2000-03-09 2003-07-31 Bowen Peter James Ballistics fire control solution process and apparatus for a spin or fin stabilised projectile
US20150101229A1 (en) * 2012-04-11 2015-04-16 Christopher J. Hall Automated fire control device
EP2645047A4 (fr) * 2010-11-22 2015-11-18 Beijing Mechanical Equipment Inst Procédé d'interception de petite cible volant à faible vitesse et à faible altitude sur la base d'un ajustement de table de tir
EP2623921A4 (fr) * 2010-09-29 2015-11-25 Beijing Mechanical Equipment Inst Procédé d'interception de petite cible à faible vitesse et à faible altitude
US9769902B1 (en) 2011-05-09 2017-09-19 The United States Of America As Represented By Secretary Of The Air Force Laser sensor stimulator
US20190154402A1 (en) * 2016-04-25 2019-05-23 Bae Systems Plc System integration
US11682535B2 (en) 2021-03-12 2023-06-20 Essex Industries, Inc. Rocker switch
US11688568B2 (en) 2021-03-15 2023-06-27 Essex Industries, Inc. Five-position switch
CN117128811A (zh) * 2023-09-14 2023-11-28 江苏北方湖光光电有限公司 具有横滚自动修正无坐力武器系统昼夜光电火控解算方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2477695A1 (fr) * 1980-03-07 1981-09-11 Giravions Dorand Procede et appareillage de commande de tir sur cible reelle
DE3128761C2 (de) * 1981-07-21 1986-01-02 Siemens AG, 1000 Berlin und 8000 München Feuerleiteinrichtung für ein Flugabwehrsystem
RU2131577C1 (ru) * 1998-05-27 1999-06-10 Конструкторское бюро приборостроения Зенитный ракетно-пушечный комплекс
RU2156943C1 (ru) * 1999-02-04 2000-09-27 ГУП "Конструкторское бюро приборостроения" Зенитная ракетно-пушечная боевая машина

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3135053A (en) * 1956-10-16 1964-06-02 Bosch Arma Corp Tracking predicting systems
US3260478A (en) * 1962-08-30 1966-07-12 Siemens Ag Albis Method and means for controlling travel motion of an object in dependence upon the position of another object
US3290992A (en) * 1964-01-15 1966-12-13 Bofors Ab Smoothing filter for a fire control system
US3309963A (en) * 1964-05-05 1967-03-21 Bofors Ab Fire control system for an antiaircraft weapon carrier
US3339457A (en) * 1964-06-26 1967-09-05 Brevets Aero Mecaniques Fire control systems
US3727514A (en) * 1968-04-25 1973-04-17 Mini Of Armed Forces Means for controlling the firing of a gun against a movable target
US3739153A (en) * 1971-08-12 1973-06-12 Hughes Aircraft Co Weapon firing computer
US3798420A (en) * 1969-06-04 1974-03-19 Rheinmetall Gmbh Method of controlling motor-driven devices adapted to be directed onto moving targets and apparatus for applying the method
US3848509A (en) * 1972-10-31 1974-11-19 Us Navy Closed-loop gun control system
US4004729A (en) * 1975-11-07 1977-01-25 Lockheed Electronics Co., Inc. Automated fire control apparatus

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3135053A (en) * 1956-10-16 1964-06-02 Bosch Arma Corp Tracking predicting systems
US3260478A (en) * 1962-08-30 1966-07-12 Siemens Ag Albis Method and means for controlling travel motion of an object in dependence upon the position of another object
US3290992A (en) * 1964-01-15 1966-12-13 Bofors Ab Smoothing filter for a fire control system
US3309963A (en) * 1964-05-05 1967-03-21 Bofors Ab Fire control system for an antiaircraft weapon carrier
US3339457A (en) * 1964-06-26 1967-09-05 Brevets Aero Mecaniques Fire control systems
US3727514A (en) * 1968-04-25 1973-04-17 Mini Of Armed Forces Means for controlling the firing of a gun against a movable target
US3798420A (en) * 1969-06-04 1974-03-19 Rheinmetall Gmbh Method of controlling motor-driven devices adapted to be directed onto moving targets and apparatus for applying the method
US3739153A (en) * 1971-08-12 1973-06-12 Hughes Aircraft Co Weapon firing computer
US3848509A (en) * 1972-10-31 1974-11-19 Us Navy Closed-loop gun control system
US4004729A (en) * 1975-11-07 1977-01-25 Lockheed Electronics Co., Inc. Automated fire control apparatus

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4266463A (en) * 1978-01-18 1981-05-12 Aktiebolaget Bofors Fire control device
US4320287A (en) * 1980-01-25 1982-03-16 Lockheed Electronics Co., Inc. Target vehicle tracking apparatus
US4528891A (en) * 1981-10-14 1985-07-16 Societe Nationale Industrielle Aerospatiale Firing control system for a direct firing weapon mounted on a rotary-wing aircraft
DE3401090C1 (en) * 1984-01-13 1991-05-02 Esg Elektronik System Gmbh Monitoring aircraft projectile or missile - using two extrapolation units to predict flight path
US4823674A (en) * 1985-08-19 1989-04-25 Saab Instruments Aktiebolag Anti-aircraft sight
US4876942A (en) * 1985-08-19 1989-10-31 Saab Instruments Aktiebolag Anti-aircraft sight
US4794235A (en) * 1986-05-19 1988-12-27 The United States Of America As Represented By The Secretary Of The Army Non-linear prediction for gun fire control systems
US4787291A (en) * 1986-10-02 1988-11-29 Hughes Aircraft Company Gun fire control system
US5420582A (en) * 1989-09-15 1995-05-30 Vdo Luftfahrtgerate Werk Gmbh Method and apparatus for displaying flight-management information
US5732289A (en) * 1993-12-28 1998-03-24 Nikon Corporation Detecting apparatus
US5900577A (en) * 1997-01-29 1999-05-04 Zdf Import Export Inc Modular, multi-caliber weapon system
US6199471B1 (en) * 1999-05-21 2001-03-13 The United States Of America As Represented By The Secretary Of The Navy Method and system for determining the probable location of a contact
US20030141364A1 (en) * 2000-03-09 2003-07-31 Bowen Peter James Ballistics fire control solution process and apparatus for a spin or fin stabilised projectile
US6776336B2 (en) * 2000-03-09 2004-08-17 Bae Systems Plc Ballistics fire control solution process and apparatus for a spin or fin stabilized projectile
EP2623921A4 (fr) * 2010-09-29 2015-11-25 Beijing Mechanical Equipment Inst Procédé d'interception de petite cible à faible vitesse et à faible altitude
EP2645047A4 (fr) * 2010-11-22 2015-11-18 Beijing Mechanical Equipment Inst Procédé d'interception de petite cible volant à faible vitesse et à faible altitude sur la base d'un ajustement de table de tir
US10271402B2 (en) 2011-05-09 2019-04-23 The United States Of America As Represented By The Secretary Of The Air Force Method of calibrating a laser sensor stimulator
US9769902B1 (en) 2011-05-09 2017-09-19 The United States Of America As Represented By Secretary Of The Air Force Laser sensor stimulator
US20150101229A1 (en) * 2012-04-11 2015-04-16 Christopher J. Hall Automated fire control device
US10782097B2 (en) * 2012-04-11 2020-09-22 Christopher J. Hall Automated fire control device
US12222191B2 (en) 2012-04-11 2025-02-11 Christopher J. Hall Automated fire control device
US11619469B2 (en) 2013-04-11 2023-04-04 Christopher J. Hall Automated fire control device
US20190154402A1 (en) * 2016-04-25 2019-05-23 Bae Systems Plc System integration
US10557686B2 (en) * 2016-04-25 2020-02-11 Bae Systems Plc System integration
US11682535B2 (en) 2021-03-12 2023-06-20 Essex Industries, Inc. Rocker switch
US11688568B2 (en) 2021-03-15 2023-06-27 Essex Industries, Inc. Five-position switch
US12046429B2 (en) 2021-03-15 2024-07-23 Essex Industries, Inc. Five-position switch
CN117128811A (zh) * 2023-09-14 2023-11-28 江苏北方湖光光电有限公司 具有横滚自动修正无坐力武器系统昼夜光电火控解算方法

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BE863223A (fr) 1978-07-24
DE2805903A1 (de) 1979-08-23
GB1568915A (en) 1980-06-11
FR2415791A1 (fr) 1979-08-24
NL7800980A (nl) 1979-07-30

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